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United States Patent |
6,202,958
|
Dommer
,   et al.
|
March 20, 2001
|
Mounting arrangement for the pivotally openable rudder blades of a guided
missile
Abstract
To maintain control accuracy for the pivotable rudder blades (14), which
lie in a combustion chamber, of a guided projectile (12) which can be
fired by means of propellent charge, there is provide a mounting
arrangement in which the trunnions (20) of the rudder blade holders (16)
of the diametrally mutually opposite rudder blades (14) are torsionally
stiffly rigidly connected through an associated coupling element (32)
which is limitedly resilient in the radial direction of the guided
projectile (12).
Inventors:
|
Dommer; Josef (Nuremburg, DE);
Schroppel; Werner (Wendelstein, DE);
Staudenmeir; Martin (Neunkirchen, DE)
|
Assignee:
|
Diehl Stiftung & Co. (Nurnberg, DE)
|
Appl. No.:
|
333605 |
Filed:
|
June 15, 1999 |
Foreign Application Priority Data
| Jun 19, 1998[DE] | 198 27 277 |
Current U.S. Class: |
244/3.28; 244/46; 244/49 |
Intern'l Class: |
F42B 010/14 |
Field of Search: |
244/3.24-3.3,46,49
|
References Cited
U.S. Patent Documents
4660786 | Apr., 1987 | Brieseck et al. | 244/3.
|
4728058 | Mar., 1988 | Brieseck et al. | 244/3.
|
5211357 | May., 1993 | Leidenberger | 244/3.
|
Foreign Patent Documents |
2410255 C2 | Oct., 1974 | DE.
| |
3441534 A1 | May., 1986 | DE.
| |
Primary Examiner: Tudor; Harold J.
Attorney, Agent or Firm: Scully, Scott, Murphy & Presser
Claims
What is claimed is:
1. A mounting arrangement for pivotally movable pairs of rudder blades (14)
of a guided missile (12) which is fired through the intermediary of a
propellent charge gas pressure, wherein each said rudder blade (14) is
mounted pivotally openable to a rudder blade holder (16) having a trunnion
(20) with a first annular shoulder (24), the trunnion (20) extending
radially into a tail structure (10) of the projectile (12), the tail
structure (10) is formed with a second annular shoulder (26), a ring
element (28) constituted of an inelastic material is arranged between the
first and second annular shoulders (24, 26) and the trunnion (20) of each
of the rudder blade holders (16) of the pair of rudder blades are axially
aligned and the trunnions (20) operatively associated therewith are
non-rotatably interconnected by a coupling element (32), wherein a spacing
between the first and second annular shoulders (24, 26) of each said
trunnion (20) and the tail structure (10) is slightly greater than the
thickness of the ring element (28) therebetween so that there is an axial
tolerance play (30) between the ring element (28) and the first and second
annular shoulders (24, 26), the minions (20) of the respective pair of
trunnions are rigidly connected to the coupling element (32), and wherein
the coupling element (32) is resilient in the radial direction of the
projectile (12).
2. A mounting arrangement according to claim 1, characterized in that each
said trunnion (20) is pinned, glued, welded or clamped to the coupling
element (32).
3. A mounting arrangement according to claim 1, characterized in that said
coupling element (32) has a pair of spaced-apart mounting end portions
(34) each connected to respectively one of said trunnions (20), and a
connecting central portion (36) which elastically resiliently connects the
two mounting end portions (34) together.
4. A mounting arrangement according to claim 3, characterized in that the
connecting central portion (36) of said coupling element (32) of two
coupling elements (32) for said mounting arrangement is provided
eccentrically in relation to the mounting end portions (34) thereof.
5. A mounting arrangement according to claim 3, characterized in that the
coupling element (32) has at one of the mounting end portion (34) a
radially outwardly extending control projection (44).
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention concerns a mounting arrangement for the pivotally openable
rudder blades, which cross each other in pairs, of a guided missile,
particularly a projectile which can be fired through the intermediary of a
propellant charge gas pressure.
2. Discussion of the Prior Art
A mounting arrangement of that kind is known from DE 34 41 534 A1. In that
known mounting arrangement, an elastically upsettable sealing ring is
provided between the one annular shoulder on the respective shaft
trunnion, and the associated second annular shoulder which is provided on
the tail structure of the missile. A sealing effect and a return function
are implemented by means of that sealing ring when the missile is launched
by means of the propellent charge. Sealing rings of that kind consisting
of elastically upsettable material however are only suitable for certain
gas pressures which are limited in an upward direction. In addition,
elastically upsettable sealing rings of that kind suffer from material
ageing which has an effect on the properties thereof in terms of
stock-keeping and durability.
Furthermore, with that known mounting arrangement of the above-described
kind, it is necessary for the shaft trunnion of the corresponding rudder
blade holder to be provided with an inclinedly extending opening into
which an associated screwthreaded pin projects in order to provide for
axial adjustment in force-locking relationship. Furthermore each shaft
trunnion is provided with the coupling element by means of a
key-and-spline connection in order to afford definedly limited radial
mobility of the respective rudder blade. All those components however
involve production tolerances which cannot be eliminated, and that has a
corresponding effect on the angular positioning of each rudder blade. In
addition the manufacture of that known mounting arrangement involves
corresponding costs. Furthermore the elastically upsettable sealing rings
result in the creation between the tail structure of the missile and the
rudder blade holders for the rudder blades of a friction which cannot be
disregarded and which has an effect on displacement of the rudder blades.
SUMMARY OF THE INVENTION
In consideration of those factors the object of the present invention is to
provide a mounting arrangement of the kind set forth in the opening part
of this specification, in which dimensional tolerances between the
components or individual parts of the mounting arrangement do not have any
influence on the angular position of the rudder blades, which is suitable
for comparatively high gas pressures of the missile which can be fired by
means of propellent charge gas pressure, which enjoys excellent
storability and in which the friction aspects are substantially reduced.
In the case of the mounting arrangement according to the invention, the
spacing between the first annular shoulder provided on the rudder blade
holder and the second annular shoulder provided on the tail structure of
the missile is slightly greater than the thickness of the ring element
which is disposed therebetween and which comprises an inelastic material,
preferably metal, so that between the ring element and the first and
second annular shoulders there is an axial tolerance play considered in
relation to the associated trunnions. That provides for the attainment of
a comparatively low level or precisely predictable degree of friction. The
respective ring element of inelastic material or metal affords the
advantage that the mounting arrangement according to the invention is not
only suitable for higher gas pressures but that in addition material
ageing is also prevented and thus storability over a longer period of time
is achieved.
The fact that, in the mounting arrangement according to the invention, the
trunnions of the respective pair of trunnions are rigidly connected to the
associated coupling element which is of a limitedly resilient nature in
the radial direction of the projectile affords the advantage that
manufacturing tolerances between the corresponding parts of the mounting
arrangement do not have any influence on the angular positioning of the
rudder blades, that is to say angular positioning of the rudder blades is
possible in a highly precise fashion in a simple manner.
The angular position of the rudder blades or the angular position of the
rudder blade holders for the rudder blades in relation to each other is
determined simply and solely by the degree of connecting accuracy between
the respective rudder blade holder and the associated trunnion. As in
accordance with the invention the trunnions of the respective pair thereof
are rigidly connected to the associated coupling element, the degree of
manufacturing accuracy of those parts advantageously has no influence on
the angular position of the rudder blade holders or the respective pair of
trunnions. That rigid connection can be implemented for example by the
respective trunnion being pinned, glued, welded or clamped to the
associated coupling element. The respective coupling element desirably has
a pair of mutually spaced mounting end portions for the associated
trunnions and a connecting central portion which radially elastically
resiliently connects the two mounting end portions. The connecting central
portion can be of a meander-shaped, arcuate, zig-zag shaped or any other
configuration, the only consideration of importance being that it is
limitedly elastically resiliently yielding in the racial direction of the
projectile.
The mounting end portions can be for example of a sleeve-shaped or
socket-shaped configuration or a journal or trunnion configuration. The
shaft trunnions of the rudder blade holders are of a configuration which
is adapted thereto. So that the connecting central portions of the two
mutually crossing coupling elements do not impair each other in respect of
their mobility, the connecting central portion of at least one of the two
coupling elements can be disposed eccentrically in relation to the
associated mounting end portions.
It will be appreciated that it is also possible for the connecting central
portions of the two coupling elements to be disposed eccentrically in
relation to the associated mounting end portions.
To provide for the defined angular setting as desired of the rudder blade
holders or the pairs of rudder blades, the respective coupling element can
be provided at one of its two mounting end portions with a control
projection which extends radially away therefrom. The respective control
projection is engaged by an actuating or drive element of a control drive
of the guided missile or projectile.
BRIEF DESCRIPTION OF THE DRAWINGS
Further details, features and advantages will be apparent from the
description hereinafter of an embodiment, illustrated by way of example in
the drawing, of the mounting arrangement according to the invention for
the pivotally openable rudder blades, which cross each other in pairs, of
a guided missile, which is in particular a projectile which can be fired
by means of propellent charge gas pressure, and essential details of the
mounting arrangement. In the drawing:
FIG. 1 is a view in longitudinal section of the tail portion of a
projectile with rudder blades which cross each other in pairs and which
are in the pivoted-open condition and which are provided on associated
rudder blade holders in such a way that they can be pivoted open,
FIG. 2 is a view on an enlarged scale of a detail from FIG. 1 for further
illustrating the rudder blade holders which are associated in pairs, with
the associated coupling element of a limitedly resilient nature, and
FIGS. 3A to 3F show various configurations of the limitedly resilient
coupling element for associated rudder blade holders as shown in FIGS. 1
and 2.
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
FIGS. 1 and 2 show a tail portion 10 of a missile 12 which has over-calibre
rudder blades 14 which are shown in their pivoted-open steering position.
Each rudder blade 14 is mounted on an associated rudder blade holder 16
pivotably about a common pivot axis 18.
Each rudder blade holder 16 has a shaft trunnion 20 which extends into the
tail structure 10 of the missile 12. The respective trunnion 20 is mounted
rotatably in the tail structure 10 by means of a bearing 22 and limitedly
movably in the radial direction of the missile 12. The trunnion 20 is
designed with a first annular shoulder 24 and the tail structure 10 is
designed adjoining the bearing 22 with a second annular shoulder 26, with
a ring element 28 being arranged between the annular shoulders. The ring
element 28 comprises an inelastic material, desirably a metal or a metal
alloy.
The spacing between the first and second annular shoulders 24 and 26 is
slightly greater than the thickness of the ring element 28 arranged
therebetween so that there is an axial tolerance play 30 between the ring
element 28 and the first and second annular shoulders 24 and 26
respectively (see in particular FIG. 2).
The trunnions 20 of the rudder blade holders 10 of the respective pair of
diametrally mutually opposite rudder blades 14 are non-rotatably connected
together by means of a coupling element 32. For that purpose the
corresponding coupling element 32 has a pair of spaced-apart mounting end
portions 34 and a connecting central portion 36 which elastically
resiliently connects the two mounting end portions 34 together. In the
embodiment shown in FIGS. 1 and 2 the respective connecting central
portion 36 is of a meander-like configuration (see also FIG. 3A or FIG.
3B). In comparison FIG. 3C shows a connecting central portion 36 which
extends in a simple angular configuration in eccentric relationship away
from the mounting portions 34. FIG. 3D shows a configuration of a coupling
element 32 in which two connecting central portions 36 which are of an
outwardly bulged angular configuration are disposed in opposite
relationship. FIG. 33 shows a configuration in which the elastically
resilient connecting central portion 36 is axially aligned with the
mounting end portions 34, the connecting central portion 36 being of a
concertina or bellows configuration. Such a coupling element 32 as shown
in FIG. 3E can be combined for example with a coupling element 32 as shown
in FIGS. 3A to 3D or with a coupling element as is illustrated in FIG. 3F
which has an arcuately bulged-out, elastically resilient connecting
central portion 36 which extends eccentrically away from the two mounting
end portions 34.
The trunnions 20 of the respective pair thereof are rigidly connected to
the associated coupling element 32. For that purpose the two mounting end
portions 34 of the respective coupling element 32 are for example of a
sleeve-shaped or socket-shaped configuration in order to receive the
corresponding end portion 38 of the respective trunnion 20. The rigid
connection between the mounting end portions 34 and the trunnions 20 is
effected for example by means of a pin 40. That rigid connection can also
be implemented by glueing, welding or clamping.
To provide for the desired setting of the rudder blades 14 in relation to
the longitudinal axis 42 of the missile 12, a control projection 44
projects radially away from the respective coupling element 32 at one of
its two mounting end portions 34 (see FIG. 1 and in particular FIG. 2).
The respective control projection 44 is for example of a forked
configuration in order to be able to mount thereto a drive or actuating
element 46 of a rudder blade control drive (not shown).
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